CN110513323B - Non-contact isolation sealing structure for turbine pump - Google Patents
Non-contact isolation sealing structure for turbine pump Download PDFInfo
- Publication number
- CN110513323B CN110513323B CN201910877788.7A CN201910877788A CN110513323B CN 110513323 B CN110513323 B CN 110513323B CN 201910877788 A CN201910877788 A CN 201910877788A CN 110513323 B CN110513323 B CN 110513323B
- Authority
- CN
- China
- Prior art keywords
- ring
- cavity
- seal
- gland
- fuel
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000007789 sealing Methods 0.000 title claims abstract description 65
- 238000002955 isolation Methods 0.000 title claims abstract description 39
- 239000000446 fuel Substances 0.000 claims abstract description 69
- 238000002485 combustion reaction Methods 0.000 claims abstract description 43
- 210000004907 gland Anatomy 0.000 claims abstract description 41
- 230000003068 static effect Effects 0.000 claims abstract description 31
- 239000011261 inert gas Substances 0.000 claims abstract description 26
- 238000005461 lubrication Methods 0.000 claims abstract description 26
- 239000007788 liquid Substances 0.000 claims abstract description 12
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 14
- 239000001301 oxygen Substances 0.000 claims description 14
- 229910052760 oxygen Inorganic materials 0.000 claims description 14
- 239000002184 metal Substances 0.000 claims description 13
- 238000007599 discharging Methods 0.000 claims description 6
- 239000002737 fuel gas Substances 0.000 claims description 5
- 238000005299 abrasion Methods 0.000 description 14
- 230000000694 effects Effects 0.000 description 13
- 239000012530 fluid Substances 0.000 description 5
- 239000007789 gas Substances 0.000 description 4
- 239000007800 oxidant agent Substances 0.000 description 4
- 238000007906 compression Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000001590 oxidative effect Effects 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/08—Sealings
- F04D29/083—Sealings especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/16—Sealings between relatively-moving surfaces
- F16J15/34—Sealings between relatively-moving surfaces with slip-ring pressed against a more or less radial face on one member
- F16J15/3436—Pressing means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/16—Sealings between relatively-moving surfaces
- F16J15/34—Sealings between relatively-moving surfaces with slip-ring pressed against a more or less radial face on one member
- F16J15/3436—Pressing means
- F16J15/3448—Pressing means the pressing force resulting from fluid pressure
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to a non-contact type isolation sealing structure for a turbine pump, which belongs to the field of mechanical sealing, and comprises an intermediate isolation seal formed by a floating ring, an intermediate shaft sleeve and a cavity, and a hydrodynamic end face lubrication seal formed by a rotating ring, a static ring, an elastic element and a gland, wherein the hydrodynamic end face lubrication seal is used for limiting leakage of fuel and combustion improver, one of two sides of the intermediate isolation seal is respectively arranged on two sides of the intermediate isolation seal, the intermediate isolation seal is used for introducing inert gas so as to isolate a small amount of fuel and combustion improver which are leaked from the hydrodynamic end face lubrication seals on two sides, the hydrodynamic end face lubrication seal on one side of the intermediate isolation seal is used for sealing low-temperature combustion improver, and the hydrodynamic end face lubrication seal on the other side of the intermediate isolation seal is used for sealing low-temperature liquid fuel.
Description
Technical Field
The invention relates to the field of mechanical sealing, in particular to a non-contact isolation sealing structure for a turbine pump.
Background
The mechanical seal is a shaft seal device of fluid rotary machinery, also called end face seal. The traditional contact type mechanical seal is fully jointed under the action of the elastic force of the compensation mechanism so as to prevent the sealing medium from leaking from the sealing end surfaces. However, mechanical seals have the disadvantages that the friction pair consisting of the dynamic and static rings is generally in a boundary friction or mixed friction state, and under the working condition of high parameters, the friction factor is large, the power consumption is high, the abrasion is serious, the service life is short, and the use and maintenance cost is high. In general, the problem with mechanical seals is mainly that the leakage of the seal is large and the wear of the end faces is large, so that the liquid fuel and the combustion improver are contacted after entering the pump from the leakage, and the efficiency of the turbine pump is reduced to a certain extent.
Disclosure of Invention
The invention aims to provide a dry gas sealing structure of a turbine pump, which reduces leakage and end face abrasion and has the advantages of reducing leakage of fuel and combustion improver, isolating the fuel from the combustion improver so that the fuel and the combustion improver are not contacted and reducing abrasion of a sealing end face.
The above object of the present invention is achieved by the following technical solutions:
the non-contact isolation sealing structure for the turbine pump comprises an intermediate isolation seal composed of a floating ring, an intermediate shaft sleeve and a cavity, and a fluid dynamic pressure end face lubrication seal composed of a rotating ring, a static ring, an elastic element and a gland and used for limiting leakage of fuel and combustion improver, wherein one fluid dynamic pressure end face lubrication seal is arranged on each side of the intermediate isolation seal;
the middle isolation seal is used for introducing inert gas to isolate a small amount of fuel and combustion improver which are leaked by lubrication and sealing of fluid dynamic pressure end surfaces at two sides, the cavity is arranged on the gland, two floating rings are arranged on the middle shaft sleeve, a gap communicated with the cavity is reserved between the two floating rings, and high-pressure inert gas enters the gap between the two floating rings from the outside through the cavity;
the dynamic pressure end face lubrication seal is arranged on one side of the middle isolation seal and used for sealing a low-temperature combustion improver, the dynamic pressure end face lubrication seal is arranged on the other side of the middle isolation seal and used for sealing low-temperature liquid fuel, the two sides of the middle shaft sleeve are respectively provided with a rotating moving ring, the static ring is fixedly arranged on the gland and is attached to the rotating moving ring, and the elastic element is arranged between the gland and the static ring, so that the static ring always has a trend of moving towards the rotating moving ring;
a through cavity is arranged between the middle isolation seal and the hydrodynamic end face lubrication seal, the through cavity comprises a first cavity channel and a second cavity channel, the first cavity channel, the second cavity channel, the cavity body and the gap are communicated, one floating ring is arranged between the gap and the first cavity channel, and the other floating ring is arranged between the gap and the second cavity channel;
the gland is provided with a first exhaust passage which is positioned on one side of the cavity and communicated with the first cavity, the first exhaust passage is used for discharging oxygen and inert gas, the gland is provided with a second exhaust passage which is positioned on the other side of the cavity and communicated with the second cavity, and the second exhaust passage is used for discharging fuel and inert gas.
By implementing the technical scheme, inert gas is pressed into the cavity, and the inert gas enters a gap between the two floating rings; in the running process of the turbine pump, the inert gas can enter the space between the floating ring and the middle shaft sleeve to generate a gas film and then enter the first cavity channel and the second cavity channel, at the moment, the floating ring and the middle shaft sleeve are separated, namely, the rotating middle shaft sleeve cannot be in direct contact with the floating ring, and the abrasion of the floating ring and the middle shaft sleeve is reduced to a certain extent. Because the joint of the rotating moving ring and the static ring is positioned at the end part of the through cavity, inert gas entering the first cavity channel and the second cavity channel can enter the end surface of the rotating moving ring opposite to the static ring under the action of pressure, and the elastic element is compressed at the moment to separate the rotating moving ring from the static ring, and after separation, the rotating moving ring is not in direct contact with the static ring, so that the end surface abrasion between the rotating moving ring and the static ring is reduced. Because inert gas is positioned between the rotating ring and the stationary ring, combustion improver at the combustion improver end and fuel at the fuel end are blocked by the inert gas and are difficult to leak into the first cavity and the second cavity, if the combustion improver at the combustion improver end is changed into oxygen to enter the first cavity and the fuel at the fuel end enters the second cavity, the inert gas existing in the first cavity and the second cavity does not react with the oxygen and the fuel but repel each other, so that the oxygen and the fuel gas can be blocked from continuously advancing, the oxygen in the first cavity can be pushed out from the first exhaust passage and the fuel in the second cavity can be pushed out from the second exhaust passage under the condition of being pressed, and the combustion improver and the fuel can not be in direct contact all the time, so that the two are completely isolated; after dry gas sealing is introduced, the leakage amount is reduced, the sealing end face of the dynamic/static ring is separated from operation, and the end face has little abrasion or no end face friction basically under the actual working condition, so that the consumption of the sealing end face of the dynamic/static ring is reduced, and the efficiency of the turbine pump is improved. Therefore, the invention can not only reduce the leakage of the fuel and the combustion improver, but also isolate the fuel from the combustion improver so that the fuel and the combustion improver are not contacted with each other, and can also achieve the effect of reducing the abrasion of the sealing end face.
Further, the elastic element comprises a corrugated pipe arranged between the gland and the stationary ring and positioned in the through cavity, a pipe seat fixedly connected with the corrugated pipe is arranged on the gland, and one end, far away from the pipe seat, of the corrugated pipe is connected with the stationary ring.
By means of the technical scheme, the corrugated pipe has scalability, compression can be achieved, the corrugated pipe is a tubular entity, and oxygen at the combustion improver end and fuel at the fuel end are not easy to leak into the through cavity through the corrugated pipe, so that the sealing effect is better.
Further, the corrugated pipe is a metal corrugated pipe.
By implementing the technical scheme, the corrugated pipe made of metal has good tolerance and long service life.
Further, a floating ring seat for limiting the position of the floating ring is arranged on the gland, the cavity is arranged at a position between the two floating ring seats on the gland, and a floating cavity is reserved between the floating ring seat and the floating ring.
By implementing the technical scheme, the floating cavity is arranged, so that the floating ring seat has a certain space for radial movement on the rotating shaft, and the floating ring and the rotating shaft can be normally separated.
Further, a rotating ring is also arranged on the rotating shaft between the fuel end and the turbine end, a tube seat is also arranged on the gland between the fuel end and the turbine end, a metal corrugated tube is arranged on the tube seat, a static ring attached to the rotating ring is also arranged on one side, far away from the tube seat, of the metal corrugated tube, and one side of the through cavity is communicated with the turbine end, and the other side of the through cavity is communicated with the attached position of the static ring and the rotating ring.
By implementing the technical scheme, the arrangement of the rotating ring and the static ring between the fuel end and the turbine end can prevent fuel in the fuel end from leaking into the turbine end to a certain extent, so that the sealing effect is achieved.
Further, sealing rings are arranged between the gland and the tube seat, between the floating ring seat and the gland, and between the rotating ring and the rotating shaft.
By means of the technical scheme, the sealing ring can further seal gaps at the connecting positions of the parts in the sealing structure, so that the overall sealing performance of the sealing structure is better.
Further, the sealing rings are all C-shaped sealing rings.
By implementing the technical scheme, the C-shaped sealing ring is a novel composite sealing element and also is a unidirectional sealing form of a metal section C-shaped structure, the contact pressure between the sealing ring and the rigid body is enhanced through the action of medium internal pressure, and in the compression process, the C-shaped sealing ring and the sealing surface are tightly combined in a linear sealing mode, so that the sealing effect is better.
Further, the end face, opposite to the stationary ring, of the rotating moving ring with the sealed hydrodynamic lubrication end face is provided with a dynamic pressure groove for liquid fuel and combustion improver to enter.
By means of the technical scheme, after the dynamic pressure grooves are formed in the end face of the rotating ring, the liquid fuel and the combustion improver can be provided with a groove cavity which exists stably, so that the liquid fuel and the combustion improver can be more stably located between the rotating ring and the static ring, the isolation effect is better, non-contact operation of the sealing end face can be achieved, and abrasion of the end face is reduced.
In summary, the invention has the following beneficial effects:
1. the invention can reduce the leakage of fuel and combustion improver, isolate the fuel from the combustion improver so as to prevent the fuel from contacting with the combustion improver, and can also achieve the effect of reducing the abrasion of the sealing end face;
2. the arrangement of the rotating ring and the stationary ring between the fuel end and the turbine end can prevent fuel in the fuel end from leaking into the turbine end to a certain extent, so that the sealing effect is achieved.
Drawings
FIG. 1 is a schematic structural view showing a sealing structure between a oxidizer end and a fuel end according to an embodiment of the present invention;
FIG. 2 is a schematic structural view for illustrating a sealing structure between a fuel end and a turbine end according to an embodiment of the present invention.
Reference numerals: 1. an intermediate sleeve; 2. dynamic pressure grooves; 21. rotating the moving ring; 3. a gland; 31. a cavity; 32. a stationary ring; 33. a first exhaust passage; 34. a second exhaust passage; 35. a tube seat; 36. a floating ring seat; 36. a floating cavity; 4. a cavity is communicated; 41. a first channel; 42. a second channel; 43. a bellows; 5. a floating ring; 51. a gap; 6. and (3) sealing rings.
Detailed Description
The technical scheme of the embodiment of the invention will be described below with reference to the accompanying drawings.
As shown in fig. 1 and 2, a non-contact type isolation seal structure for a turbo pump includes an intermediate isolation seal composed of a floating ring 5, an intermediate sleeve 1 and a cavity 31, and hydrodynamic end face lubrication seals composed of a rotating ring 21, a stationary ring 32, an elastic member and a gland 3 for restricting leakage of fuel and oxidizer, the hydrodynamic end face lubrication seals being provided with one on each side of the intermediate isolation seal (in this embodiment, divided into a oxidizer end, a fuel end and a turbine end in this order in the length direction of the intermediate sleeve 1);
the middle isolation seal is used for introducing inert gas to isolate a small amount of fuel and combustion improver which are leaked by the lubrication seal of the hydrodynamic end surfaces at two sides, the cavity 31 is arranged on the gland 3, two floating rings 5 are arranged on the middle shaft sleeve 1, a gap 51 communicated with the cavity 31 is reserved between the two floating rings 5, and high-pressure inert gas enters the gap 51 between the two floating rings 5 from the outside through the cavity 31;
as shown in fig. 1 and 2, the hydrodynamic end face lubrication seal located at one side of the middle isolation seal is used for sealing the low-temperature combustion improver, the hydrodynamic end face lubrication seal located at the other side of the middle isolation seal is used for sealing the low-temperature liquid fuel, the rotating moving ring 21 is respectively provided with one on two sides of the middle shaft sleeve 1, the static ring 32 is fixedly arranged on the gland 3 and is attached to the rotating moving ring 21, and the elastic element is arranged between the gland 3 and the static ring 32, so that the static ring 32 always has a trend of moving towards the rotating moving ring 21; the elastic element is a corrugated pipe 43 arranged between the gland 3 and the stationary ring 32 and positioned in the through cavity 4, the gland 3 is provided with a pipe seat 35 fixedly connected with the corrugated pipe 43, one end of the corrugated pipe 43 away from the pipe seat 35 is connected with the stationary ring 32, and the corrugated pipe 43 is a metal corrugated pipe 43.
Because the bellows 43 itself has scalability, can realize compressing to bellows 43 is the tubular entity, and the oxygen of oxidant end and the fuel of fuel end are difficult for leaking through bellows 43 department and lead to in the chamber 4, thereby make sealed effect better, and bellows 43 that the metal was made is tolerated better, longe-lived.
As shown in fig. 1 and 2, a through cavity 4 is arranged between the intermediate isolation seal and the hydrodynamic end face lubrication seal, the through cavity 4 comprises a first cavity channel 41 and a second cavity channel 42, the first cavity channel 41, the second cavity channel 42, the cavity 31 and the gap 51 are arranged in a communicating manner, one floating ring 5 is arranged between the gap 51 and the first cavity channel 41, and the other floating ring 5 is arranged between the gap 51 and the second cavity channel 42.
As shown in fig. 1 and 2, a first exhaust passage 33 communicated with a first cavity channel 41 is formed on one side of the cavity 31 on the gland 3, the first exhaust passage 33 is used for discharging oxygen and inert gas, a second exhaust passage 34 communicated with a second cavity channel 42 is formed on the other side of the cavity 31 on the gland 3, and the second exhaust passage 34 is used for discharging fuel and inert gas; the gland 3 is provided with a floating ring seat 36 for limiting the position of the floating ring 5, the cavity 31 is arranged at a position between the two floating ring seats 36 on the gland 3, a floating cavity 37 is reserved between the floating ring seat 36 and the floating ring 5, and the floating cavity 37 can enable the floating ring seat 36 to have a certain space for radial movement on a rotating shaft, so that the floating ring 5 and the rotating shaft can be normally separated.
As shown in fig. 1 and 2, a rotating ring 21 is also arranged on the rotating shaft between the fuel end and the turbine end, a tube seat 35 is also arranged on the gland 3 between the fuel end and the turbine end, a metal corrugated tube 43 is arranged on the tube seat 35, a static ring 32 attached to the rotating ring 21 is also arranged on one side of the metal corrugated tube 43 away from the tube seat 35, one side of the through cavity 4 is communicated with the turbine end, the other side of the through cavity is communicated with the attachment position of the static ring 32 and the rotating ring 21, and the arrangement of the rotating ring 21 and the static ring 32 between the fuel end and the turbine end can prevent fuel in the fuel end from leaking into the turbine end to a certain extent, so that the sealing effect is achieved.
As shown in fig. 1 and 2, sealing rings 6 are arranged between the gland 3 and the tube seat 35, between the floating ring seat 36 and the gland 3 and between the rotating ring 21 and the rotating shaft, and the sealing rings 6 are C-shaped sealing rings 6; the setting of sealing washer 6 can further seal the gap of part junction in the seal structure to make the holistic sealing performance of seal structure better, and C type sealing washer 6 is a novel compound seal element, also is the one-way sealed form of a metal cross-section C shape structure, and it forms the contact pressure between reinforcing sealing washer 6 and the rigid body through the effect of medium internal pressure, in the compression process, makes C type sealing washer 6 and sealed face closely combine with the line sealing mode, thereby lets sealed effect better.
As shown in fig. 1 and 2, a dynamic pressure groove 2 for liquid fuel and combustion improver to enter is formed on the end surface of a rotating moving ring 21, which is sealed by the fluid dynamic pressure lubrication end surface and is opposite to a stationary ring 32; after the dynamic pressure groove 2 is formed on the end face of the rotating ring 21, the liquid fuel and the combustion improver can be provided with a groove cavity which exists stably, so that the liquid fuel and the combustion improver can be more stably positioned between the rotating ring 21 and the static ring 32, the isolation effect is better, the non-contact operation of the sealing end face can be realized, and the abrasion of the end face is reduced.
The specific working process comprises the following steps: the inert gas is pressed into the cavity 31 and enters the gap 51 between the two floating rings 5; during the operation of the turbine pump, the inert gas enters the space between the floating ring 5 and the middle shaft sleeve 1 to generate a gas film and then enters the first cavity channel 41 and the second cavity channel 42, and at this time, the floating ring 5 and the middle shaft sleeve 1 are separated, i.e. the rotating middle shaft sleeve 1 is not in direct contact with the floating ring 5, so that the abrasion of the floating ring 5 and the middle shaft sleeve is reduced to a certain extent. Since the joint of the rotating ring 21 and the stationary ring 32 is located at the end of the through cavity 4, inert gas entering the first cavity channel 41 and the second cavity channel 42 can enter the end face of the rotating ring 21 opposite to the stationary ring 32 under the action of pressure, and the elastic element is compressed at the moment to separate the rotating ring 21 from the stationary ring 32, and after separation, the rotating ring 21 is not in direct contact with the stationary ring 32, so that the end face abrasion between the rotating ring 21 and the stationary ring 32 is reduced. Because the inert gas is located between the rotating ring 21 and the stationary ring 32, the combustion improver at the combustion improver end and the fuel at the fuel end are blocked by the inert gas, so that the combustion improver is difficult to leak into the first cavity channel 41 and the second cavity channel 42, if some combustion improver at the combustion improver end becomes oxygen to enter the first cavity channel 41 and the fuel at the fuel end enters the second cavity channel 42, the inert gas existing in the first cavity channel 41 and the second cavity channel 42 does not react with the oxygen and the fuel, but repels each other, so that the oxygen and the fuel gas can be prevented from continuously advancing, the oxygen in the first cavity channel 41 can be pushed out from the first exhaust channel 33, the fuel in the second cavity channel 42 can be pushed out from the second exhaust channel 34 under the condition of being pressed, and the combustion improver and the fuel can not be directly contacted all the time, so that the oxygen and the fuel are completely isolated; namely, after the isolation seal is introduced, the leakage amount is reduced, the sealing end face of the dynamic/static ring 32 is separated from operation, and the end face has little abrasion or basically no end face friction under the actual working condition, so that the consumption of the sealing end face of the dynamic/static ring 32 is reduced, and the efficiency of the turbine pump is improved. Therefore, the invention can not only reduce the leakage of the fuel and the combustion improver, but also isolate the fuel from the combustion improver so that the fuel and the combustion improver are not contacted with each other, and can also achieve the effect of reducing the abrasion of the sealing end face.
Claims (6)
1. The non-contact isolation sealing structure for the turbine pump is characterized by comprising an intermediate isolation seal composed of a floating ring (5), an intermediate shaft sleeve (1) and a cavity (31), and a hydrodynamic end face lubrication seal composed of a rotating ring (21), a static ring (32), an elastic element and a gland (3) and used for limiting leakage of fuel and combustion improver, wherein one hydrodynamic end face lubrication seal is arranged on each side of the intermediate isolation seal;
the middle isolation seal is used for introducing inert gas to isolate a small amount of fuel and combustion improver which are leaked by the hydrodynamic end face lubrication seal at two sides, the cavity (31) is formed on the gland (3), two floating rings (5) are arranged on the middle shaft sleeve (1), a gap (51) communicated with the cavity (31) is reserved between the two floating rings (5), and high-pressure inert gas enters the gap (51) between the two floating rings (5) from the outside through the cavity (31);
the hydrodynamic end face lubrication seal positioned on one side of the middle isolation seal is used for sealing a low-temperature combustion improver, the hydrodynamic end face lubrication seal positioned on the other side of the middle isolation seal is used for sealing low-temperature liquid fuel, the two sides of the middle shaft sleeve (1) of the rotating moving ring (21) are respectively provided with one static ring (32), the static ring (32) is fixedly arranged on the gland (3) and is attached to the rotating moving ring (21), and the elastic element is arranged between the gland (3) and the static ring (32) and enables the static ring (32) to always have a trend of moving towards the side of the rotating moving ring (21);
a through cavity (4) is arranged between the middle isolation seal and the hydrodynamic end face lubrication seal, the through cavity (4) comprises a first cavity channel (41) and a second cavity channel (42), the first cavity channel (41), the second cavity channel (42), the cavity (31) and the gap (51) are communicated, one floating ring (5) is arranged between the gap (51) and the first cavity channel (41), and the other floating ring (5) is arranged between the gap (51) and the second cavity channel (42);
a first exhaust passage (33) communicated with a first cavity passage (41) is formed in one side of the cavity (31) on the gland (3), the first exhaust passage (33) is used for discharging oxygen and inert gas, a second exhaust passage (34) communicated with a second cavity passage (42) is formed in the other side of the cavity (31) on the gland (3), and the second exhaust passage (34) is used for discharging fuel and inert gas;
the elastic element comprises a corrugated pipe (43) arranged between the gland (3) and the stationary ring (32) and positioned in the through cavity (4), a pipe seat (35) fixedly connected with the corrugated pipe (43) is arranged on the gland (3), and one end, far away from the pipe seat (35), of the corrugated pipe (43) is connected with the stationary ring (32);
the end face, opposite to the stationary ring (32), of the rotating moving ring (21) with the sealed hydrodynamic lubrication end face is provided with dynamic pressure grooves (2) for liquid fuel and combustion improver to enter.
2. A non-contact isolation seal for a turbo pump according to claim 1, wherein: the corrugated pipe (43) is a metal corrugated pipe (43).
3. A non-contact isolation seal for a turbo pump according to claim 1, wherein: the gland (3) is provided with a floating ring seat (36) for limiting the position of the floating ring (5), the cavity (31) is arranged at a position between the two floating ring seats (36) on the gland (3), and a floating cavity (37) is reserved between the floating ring seat (36) and the floating ring (5).
4. A non-contact isolation seal for a turbo pump according to claim 3, wherein: the rotary ring (21) is also arranged on the rotary shaft between the fuel end and the turbine end, the tube seat (35) is also arranged on the gland (3) between the fuel end and the turbine end, the metal corrugated tube (43) is arranged on the tube seat (35), the stationary ring (32) attached to the rotary ring (21) is also arranged on one side, far away from the tube seat (35), of the metal corrugated tube (43), and one side of the through cavity (4) is communicated with the turbine end, and the attached position of the stationary ring (32) and the rotary ring (21) is communicated with the other side.
5. A non-contact isolation seal for a turbo pump according to claim 4, wherein: sealing rings (6) are arranged between the gland (3) and the tube seat (35), between the floating ring seat (36) and the gland (3) and between the rotating ring (21) and the rotating shaft.
6. A non-contact isolation seal for a turbo pump according to claim 5, wherein: the sealing rings (6) are C-shaped sealing rings (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910877788.7A CN110513323B (en) | 2019-09-17 | 2019-09-17 | Non-contact isolation sealing structure for turbine pump |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910877788.7A CN110513323B (en) | 2019-09-17 | 2019-09-17 | Non-contact isolation sealing structure for turbine pump |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110513323A CN110513323A (en) | 2019-11-29 |
| CN110513323B true CN110513323B (en) | 2024-02-20 |
Family
ID=68632464
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910877788.7A Active CN110513323B (en) | 2019-09-17 | 2019-09-17 | Non-contact isolation sealing structure for turbine pump |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110513323B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113124163B (en) * | 2021-04-29 | 2023-10-24 | 西安航天动力研究所 | Symmetrical low-temperature-resistant combined sealing device |
| CN113090575B (en) * | 2021-05-12 | 2022-07-19 | 西安航天动力研究所 | Double-floating-ring sealing blowing isolation device and turbopump |
| CN117646797B (en) * | 2024-01-30 | 2024-05-14 | 中密控股股份有限公司 | Sealing suitable for coolant circulating pump of ship power device |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0032433A1 (en) * | 1980-01-11 | 1981-07-22 | Ae Plc | Means for cooling positive clearance radial face seals |
| CN201771838U (en) * | 2010-07-08 | 2011-03-23 | 中国航天科技集团公司第六研究院第十一研究所 | Sealing structure of turbine pump |
| JP2012117432A (en) * | 2010-11-30 | 2012-06-21 | Nippon Pillar Packing Co Ltd | Shaft seal device for submerged pump |
| CN108426035A (en) * | 2018-05-18 | 2018-08-21 | 四川日机密封件股份有限公司 | A kind of enhanced non-contact mechanical seal structure of liquid |
| CN108757945A (en) * | 2018-06-20 | 2018-11-06 | 西安交通大学 | A kind of hybrid lubrication end face seal structure |
| JP2019039417A (en) * | 2017-08-29 | 2019-03-14 | 株式会社荏原製作所 | Seal system |
| CN109737094A (en) * | 2018-11-13 | 2019-05-10 | 陕西蓝箭航天技术有限公司 | Dynamic sealing device and gas-turbine-pump combination for turbine pump |
| CN210769495U (en) * | 2019-09-17 | 2020-06-16 | 中密控股股份有限公司 | Non-contact isolation sealing structure for turbine pump |
-
2019
- 2019-09-17 CN CN201910877788.7A patent/CN110513323B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0032433A1 (en) * | 1980-01-11 | 1981-07-22 | Ae Plc | Means for cooling positive clearance radial face seals |
| CN201771838U (en) * | 2010-07-08 | 2011-03-23 | 中国航天科技集团公司第六研究院第十一研究所 | Sealing structure of turbine pump |
| JP2012117432A (en) * | 2010-11-30 | 2012-06-21 | Nippon Pillar Packing Co Ltd | Shaft seal device for submerged pump |
| JP2019039417A (en) * | 2017-08-29 | 2019-03-14 | 株式会社荏原製作所 | Seal system |
| CN108426035A (en) * | 2018-05-18 | 2018-08-21 | 四川日机密封件股份有限公司 | A kind of enhanced non-contact mechanical seal structure of liquid |
| CN108757945A (en) * | 2018-06-20 | 2018-11-06 | 西安交通大学 | A kind of hybrid lubrication end face seal structure |
| CN109737094A (en) * | 2018-11-13 | 2019-05-10 | 陕西蓝箭航天技术有限公司 | Dynamic sealing device and gas-turbine-pump combination for turbine pump |
| CN210769495U (en) * | 2019-09-17 | 2020-06-16 | 中密控股股份有限公司 | Non-contact isolation sealing structure for turbine pump |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110513323A (en) | 2019-11-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110513323B (en) | Non-contact isolation sealing structure for turbine pump | |
| CN107387261B (en) | Combined mechanical sealing device | |
| CN107588038B (en) | Mechanical sealing structure of turbine pump | |
| CN107939722B (en) | Spring-loaded automatic release type dynamic sealing device for oxyhydrogen engine turbopump | |
| CN105422863A (en) | Combined type sealing device for liquid oxygen pump | |
| CN109162955A (en) | Combine automatic disengaging dynamic sealing device in a kind of engine turbine pumps labyrinth | |
| CN100389271C (en) | High performance water lubricating mechanical driving system | |
| CN210769495U (en) | Non-contact isolation sealing structure for turbine pump | |
| CN201771834U (en) | Sealing structure of turbopump assembly | |
| CN104565363B (en) | Combined type sealing device for low-temperature engine oxidizing agent | |
| CN102900846A (en) | Novel sealing device combining Archimedes spiral groove sealing and contact type mechanical sealing | |
| CN102865369B (en) | A kind of fluctuate hermetical ring with static pressure and dynamic pressure double effect | |
| CN111810642A (en) | Dynamic sealing structure suitable for low-pressure small-motion-amplitude working condition | |
| CN112012954B (en) | Turbo pump sealing mechanism and turbo pump | |
| CN212564389U (en) | Mechanical sealing element | |
| CN205639619U (en) | Combined sealing device for liquid oxygen pump | |
| CN109441709B (en) | Compact type large-torque anti-pollution gear hydraulic motor | |
| CN114542327B (en) | Mechanical sealing device for liquid oxygen pump | |
| CN112431756A (en) | Sealing structure of duplex gear pump with clearance compensation function | |
| CN107355537B (en) | Carbon float sealing ring with fluid groove and sealing device thereof | |
| CN218991952U (en) | Mechanical sealing device for emulsion pump | |
| CN216894857U (en) | Plunger pump adopting coupling self-sealing packing | |
| CN219605487U (en) | Inclined shaft plunger pump | |
| CN217422175U (en) | Novel flange seal structure in high-pressure valve | |
| CN220910473U (en) | Radial compound oil blanket of two-way maze |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB02 | Change of applicant information |
Address after: 610041 No.8, Wuke West 4th Road, Wuhou District, Chengdu, Sichuan Province Applicant after: Zhongmi Holding Co.,Ltd. Address before: 610041 No.8, Wuke West 4th Road, Wuhou District, Chengdu, Sichuan Province Applicant before: SICHUAN SUNNY SEAL Co.,Ltd. |
|
| CB02 | Change of applicant information | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |